The optimal ascent problem for a hypersonic vehicle is formulated as an inverse dynamic problem. This formulation is essential in solving the trajectory optimization problem via the nonlinear programming approach. Both minimum-fuel and minimax type of performance indices are considered. The results reveal important features of the optimal trajectory and controls, and they are subsequently used to construct a nonlinear feedback midcourse control law. This control law not only greatly simplifies the difficult constrained optimization problem and yields improved solutions, but is also suitable for onboard implementation. Finally, off-nominal trajectory guidance is addressed using combination of feedback compensation and onboard generation of control through the inverse dynamics approach.


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    Title :

    Trajectory optimization and guidance for a hypersonic vehicle


    Contributors:
    Lu, Ping (author)

    Publication date :

    1991-12-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English


    Keywords :




    Trajectory Optimization for Hypersonic Aircraft Guidance

    Schultz, R. L. / Hoffman, M. J. / Case, A. M. et al. | British Library Conference Proceedings | 1992


    Trajectory Optimization for Hypersonic Aircraft Guidance

    R. L. Schultz / M. J. Hoffman / A. M. Case et al. | NTIS | 1992